CN204591487U - A kind of aircraft engine intake deicing system - Google Patents
A kind of aircraft engine intake deicing system Download PDFInfo
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- CN204591487U CN204591487U CN201520070355.8U CN201520070355U CN204591487U CN 204591487 U CN204591487 U CN 204591487U CN 201520070355 U CN201520070355 U CN 201520070355U CN 204591487 U CN204591487 U CN 204591487U
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Abstract
A kind of aircraft engine intake deicing system belongs to Flight Vehicle Design and manufacture field, comprises engine inlets, adopts hot-gas system, air collecting pipe, outlet pipe, and engine inlets are designed to interlayer; The design of gas production hole is on the exhaust duct of airplane engine.The utility model utilizes the hot gas of engine exhaust conduit to carry out anti-ice operation to the intake duct of airplane engine, overcome the shortcoming that hot gas deicing takes hot gas to cause engine performance to change from engine compressor, deicing is effective, structure is simple, easy to operate, be applicable to the aircraft of various model or specification, greatly can improve the safety index of aircraft under severe weather conditions, prevent the flying accident caused because of engine inlets structure.
Description
Technical field
The utility model belongs to Flight Vehicle Design and manufacture field, is specifically related to a kind of engine inlets deicing system of aircraft.
Background technique
When aircraft flies under icing meteorology condition, some parts windward surface will with the droplets impact its in air, gather and freeze.A large amount of accidents and research all show that even the accumulated ice of aircraft key position, a small amount of, also can cause the lift of aircraft to decline, flight resistance increase, thus cause the deterioration of the pneumatic qualities such as the maneuverability of aircraft and stability.Engine inlets and air inlet component freeze, destroy the aerodynamic configuration of airplane design, reduce intake duct area, also reduce ventilation area between the every adjacent blades of gas compressor of airplane engine simultaneously, make to enter engine air capacity and reduce, thus engine power declines.In order to ensure rotating speed and the thrust of motor, at this moment must strengthen fuel oil specific discharge, like this except increase fuel oil specific consumption, turbine entrance temperature temperature also can be made to raise, if exceed permitted value, can turbine blade be burnt out, cause engine cut-off.
And due to freeze nonsymmetry and compressor blade on the uneven of ice sheet come off, the dynamic balancing of rotor is destroyed in capital, it is except causing the vibration of power plant and aircraft, the damage of engine bearing also can be caused time serious, the ice sheet come off enters gas compressor with high velocity air, beats and gas compressor also may be caused to damage on blade.Therefore the research carrying out aircraft anti-icing technology is the very important importance of aircraft, significant to aircraft safety.
For the different parts of aircraft, current anti-icing method has:
1. from the hot gas anti-icing system of engine bleed air
Be mainly used in the anti-icing of wing, empennage leading edge and engine inlets lip and air inlet component, make the temperature of protection coating reach the evaporating temperature of super-cooling waterdrop under ice-formation condition by the heating of hot gas, thus avoid super-cooling waterdrop to freeze to freeze at frozen surface.
2. cycle air sac type deicing system
Utilize engine bleed to supply air bag pneumatic channel, make it periodically to expand or shrink, destroy the combination force of ice sheet and aircraft surfaces, then be issued to the object of deicing in the effect of aerodynamic force.Be mainly used in the deicing of wing, empennage leading edge, the bleed of needs is much little compared with hot gas anti-icing system, when anti-icing hot gas undersupply, can be used as alternative icing protective measures.
3. electro thermal ice protection system
Anti-ice action can be played by continuous heating, can heat as deicing system in the cycle again.Be mainly used in the anti-icing of propeller blade, rectification calotte and windscreen.
4.TKS system
The aerofoil of western sharp SR22 is anti-icing all to be adopted in this way.Arrange at main wing and empennage leading edge and entirely open up anti-icer shoes, anti-icer shoes directly makes stainless steel leading edge, anti-icing surface all adopts laser micropore processes, these micropores we visually see less than, an anti-freeze fluid case is had at left main wing root, anti-freeze fluid is covered with whole leading edge by oozing out from these micropores of full exhibition anti-icer shoes after suction booster supercharging, thus reaches anti-icing object.
Except above-mentioned electric heating system, the electricity of low energy consumption scolds deicing, Electro-Impulse De-icing and other novel anti-icing method, also the anti-icing replacement scheme of bleed is can be used as having children outside the state plan ripple, marmem and high-frequency electronic deicing etc., the key technology of these schemes, still in exploitation and experimental stage, needs in use to verify its feasibility and reliability further.
Except the method for these initiatively deicing above-mentioned, also extensively adopt in the world at present and play passive anti-icing effect in easily the freeze method of position application low-surface-energy hydrophobic coating of aircraft.This coating, except reducing the condensation degree of super-cooling waterdrop at body surface, when aircraft is by heating active deicing, can also makes body surface ice sheet melt the water droplet formed and depart from body as early as possible, thus prevent from heavily freezing.The relatively aforementioned several method of this method have cost low, consume energy little, realize the features such as difficulty is low, be the anti-deicing supplementary means of a kind of very important aircraft surfaces.But the performance of current most of low-surface-energy hydrophobic coatings still can not meet the safety requirement of the anti-deicing of aircraft surfaces completely.
Wherein, hot air anti-icing and electro-thermal anti-ice have overwhelming superiority in anti-icing system.It is less or use the parts of hot air anti-icing inconvenience that electro-thermal anti-ice is generally applicable to power, as windshield thermometric pressure measurement probe, if there are the larger portion parts such as propeller cavitation, then adopts periodically electro thermal ice protection system alternately to heat.And electro thermal ice protection system more complicated, heating element manufacture is more difficult, and wire and heating element likely burn out, maintenance work more complicated; The hot air anti-icing of engine compressor, controls more difficult, little employing cycle hot gas anti-icing system, and efficiency is not high.For the deicing of engine inlets leading edge, what generally adopt is the hot air anti-icing of engine bleed air.The subject matter existed is that anti-icing system work is from bleed in engine compressor, and therefore the characteristic of motor may change, and the thrust of motor can be caused to reduce.Engine compressor flow reduces also may cause compressor stall, makes compressor blade produce alternating stress and cause tired impaired.
Model utility content
Adopt from the hot gas engine compressor for solving hot air anti-icing in prior art, cause affecting the service behaviour of motor and the high technical problem of energy consumption, the utility model provides a kind of directly gas production from waste pipe, the intake duct of motor is carried out to the system of deicing.
A kind of aircraft engine intake deicing system, comprises engine inlets, adopts hot-gas system, air collecting pipe, outlet pipe, it is characterized in that: described engine inlets are designed to closed sandwich; Described hot-gas system of adopting comprises gas production hole, airtight plate, airtight plate controlling component, the design of gas production hole is on the exhaust duct of airplane engine, block up when airtight plate is normally closed and be connected on gas production hole place, airtight plate is connected with the controlling component of airtight plate, and airtight plate realizes the opening and closing of airtight plate under the control of airtight plate controlling component, when airtight plate is opened, airtight plate probes into engine exhaust pipe and engine exhaust pipe gas is imported gas production hole; Air collecting pipe is tightly connected with the gas production hole of adopting hot-gas system; The other end of air collecting pipe is fixed on engine inlets sandwich shell, and engine inlets sandwich shell opposite side, is designed with exhaust port, and exhaust port is connected with heat extraction tracheae, and heat extraction tracheae is connected with engine exhaust pipe.
The utility model utilizes the hot gas of engine exhaust conduit to carry out anti-ice operation to the intake duct of airplane engine, overcome the shortcoming that hot gas deicing takes hot gas to cause engine performance to change from engine compressor, deicing is effective, structure is simple, easy to operate, be applicable to the aircraft of various model or specification, greatly can improve the safety index of aircraft under severe weather conditions, prevent the flying accident caused because of engine inlets structure.
Accompanying drawing explanation
Fig. 1: adopt hot-gas system structural representation;
Fig. 2: engine inlets deicing function structural representation
In figure: 1. air collecting pipe 2. airtight plate 3. rotating shaft 4. pull bar 5. engine exhaust pipe 6. cable wire 7. heat extraction tracheae
Embodiment
Below in conjunction with accompanying drawing, the utility model is made an explanation:
A kind of aircraft engine intake deicing system, comprises engine inlets, adopts hot-gas system, air collecting pipe 1, outlet pipe, it is characterized in that: described engine inlets are designed to closed sandwich; Described hot-gas system of adopting comprises gas production hole, airtight plate 2, airtight plate 2 controlling component, the design of gas production hole is on the exhaust duct of airplane engine, airtight plate 2 blocks up time normally closed and is connected on gas production hole place, airtight plate 2 is connected with the controlling component of airtight plate 2, and airtight plate 2 realizes the opening and closing of airtight plate 2 under the control of airtight plate 2 controlling component, when airtight plate 2 is opened, airtight plate 2 probes into engine exhaust pipe 5 and engine exhaust pipe 5 gas is imported gas production hole; Air collecting pipe 1 is tightly connected with the gas production hole of adopting hot-gas system; The other end of air collecting pipe 1 is fixed on engine inlets sandwich shell, and engine inlets sandwich shell opposite side, is designed with exhaust port, and exhaust port is connected with heat extraction tracheae, and heat extraction tracheae is connected with engine exhaust pipe 5.
For making control more convenient, described airtight plate 2 controlling component comprises handle, pull bar 4, cable wire 6, rotating shaft 3, described handle is arranged in aircraft cockpit, handle is connected with cable wire 6, the other end of cable wire 6 is connected with pull bar 4, the other end of pull bar 4 is fixed with rotating shaft 3, and described rotating shaft 3 axis body is fixed on the control end of airtight plate 2 through air collecting pipe 1 tube wall.In passenger cabin, pull handle during use, then cable wire 6 drives pull bar 4, and pull bar 4 rotates, the rotating shaft 3 be fixed on pull bar 4 rotates, and then rotating shaft 3 drives airtight plate 23 rotations around the shaft, airtight plate 2 screws in waste pipe, and stop portions gas enters in air collecting pipe 1; Release handle, then cable wire 6 drives pull bar 4 to return position, then rotating shaft 3 and airtight plate 2 also return normally off thereupon.
Above-mentioned airtight plate 2 control gear is all controlled by cable wire 6, then likely at the air flow resistance of airtight plate 2 by engine exhaust pipe 5 road, can not return normally off in time, complete heating ice detachment by operation.For the airtight plate 2 solving deicing system above-mentioned reclaims, return the technical problem of normally off, the utility model is also designed with restoring spring, and described restoring spring one end is fixed, and elastic force end is connected with pull bar 4; Pull cable wire 6, then pull bar 4 overcomes spring force 3 rotations around the shaft, drives airtight plate 2 to rotate, thus airtight plate 2 is opened, in air collecting pipe 1, import hot gas; Unclamp cable wire 6, then rotating shaft 3 is under the effect of spring force, pulls pull bar 4 to playback fast.
Described restoring spring elastic force end and the tie point of pull bar 4 can design at pull bar 4 lengthwise centers to the position between pull bar 4 and cable wire 6 joint.This design makes restoring spring provide less power just can realize airtight plate 2 to keep in the center, and the release of restoring spring elastic force is complete, and airtight plate 2 is in normally off.
For making the air-flow in engine inlets interlayer fully contact with shell, in engine inlets interlayer, be designed with the channel-shaped guide plate that cross section is U-shaped, guide plate is fixed in intake duct interlayer.The hot gas that air collecting pipe 1 imports circulates in interlayer along guide plate, realizes the heating deicing to engine inlets.
The suction port design of described engine inlets interlayer, at the opening wooden partition outer side surface of U-shaped guide plate, after the hot gas of suction port enters interlayer, forms hot air flow along between guide plate and sandwich shell; Vent design is at another outer side surface of U-shaped guide plate opening wooden partition.This design ensures that the utilization ratio of hot gas is higher, and can not form hot gas eddy current in interlayer, greatly can improve deicing efficiency.
Protection domain of the present utility model is not limited only to the technological scheme disclosed in embodiment part, and all operating elements that utilizes all fall into protection domain of the present utility model from the exhaust duct heat-obtaining gas of aircraft to the device that the intake duct of airplane engine carries out deicing.
Claims (6)
1. an aircraft engine intake deicing system, comprises engine inlets, adopts hot-gas system, air collecting pipe (1), outlet pipe, it is characterized in that: described engine inlets are designed to closed sandwich, described hot-gas system of adopting comprises gas production hole, airtight plate (2), airtight plate (2) controlling component, the design of gas production hole is on the exhaust duct of airplane engine, block up when airtight plate (2) is normally closed and be connected on gas production hole place, airtight plate (2) is connected with the controlling component of airtight plate (2), and airtight plate (2) realizes the opening and closing of airtight plate (2) under the control of airtight plate (2) controlling component, when airtight plate (2) is opened, airtight plate (2) probes into engine exhaust pipe (5) and engine exhaust pipe (5) gas is imported gas production hole, air collecting pipe (1) is tightly connected with the gas production hole of adopting hot-gas system, the other end of air collecting pipe (1) is fixed on engine inlets sandwich shell, and engine inlets sandwich shell opposite side, is designed with exhaust port, and exhaust port is connected with heat extraction tracheae, and heat extraction tracheae is connected with engine exhaust pipe (5).
2. a kind of aircraft engine intake deicing system according to claim 1, it is characterized in that: described airtight plate (2) controlling component comprises handle, pull bar (4), cable wire (6), rotating shaft (3), described handle is arranged in aircraft cockpit, handle is connected with cable wire (6), the other end of cable wire (6) is connected with pull bar (4), the other end of pull bar (4) is fixed with rotating shaft (3), and described rotating shaft (3) axis body is fixed on the control end of airtight plate (2) through air collecting pipe (1) tube wall.
3. a kind of aircraft engine intake deicing system according to claim 2, is characterized in that: be also designed with restoring spring, and described restoring spring one end is fixed, and elastic force end is connected with pull bar (4); Pull cable wire (6), then pull bar (4) overcomes spring force (3) rotation around the shaft, drive airtight plate (2) to rotate, thus airtight plate (2) is opened, in air collecting pipe (1), import hot gas; Unclamp cable wire (6), then rotating shaft (3), under the effect of spring force, pulls pull bar (4) to playback fast.
4. a kind of aircraft engine intake deicing system according to claim 3, it is characterized in that: the tie point of described restoring spring elastic force end and pull bar (4) can design at pull bar (4) lengthwise centers to the position between pull bar (4) and cable wire (6) joint, this design makes restoring spring provide less power just can realize airtight plate (2) to keep in the center, the release of restoring spring elastic force is complete, and airtight plate (2) is in normally off.
5. a kind of aircraft engine intake deicing system according to the arbitrary claim of claim 1,2,3,4, it is characterized in that: fully contact with shell for making the air-flow in engine inlets interlayer, in engine inlets interlayer, be designed with the channel-shaped guide plate that cross section is U-shaped, guide plate is fixed in intake duct interlayer.
6. a kind of aircraft engine intake deicing system according to claim 5, it is characterized in that: the suction port of described engine inlets interlayer designs the opening wooden partition outer side surface at U-shaped guide plate, after the hot gas of suction port enters interlayer, form hot air flow along between guide plate and sandwich shell; Vent design is at another outer side surface of U-shaped guide plate opening wooden partition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520070355.8U CN204591487U (en) | 2015-01-30 | 2015-01-30 | A kind of aircraft engine intake deicing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520070355.8U CN204591487U (en) | 2015-01-30 | 2015-01-30 | A kind of aircraft engine intake deicing system |
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| CN204591487U true CN204591487U (en) | 2015-08-26 |
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| CN201520070355.8U Expired - Fee Related CN204591487U (en) | 2015-01-30 | 2015-01-30 | A kind of aircraft engine intake deicing system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104727945A (en) * | 2015-01-30 | 2015-06-24 | 江苏中陆航星航空工业有限公司 | De-icing system of aircraft engine inlet |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
-
2015
- 2015-01-30 CN CN201520070355.8U patent/CN204591487U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104727945A (en) * | 2015-01-30 | 2015-06-24 | 江苏中陆航星航空工业有限公司 | De-icing system of aircraft engine inlet |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150826 Termination date: 20160130 |
|
| EXPY | Termination of patent right or utility model |